An aero-engine casing integrating bearing and mounting functions

Abstract

The application provides an aero-engine casing integrating support and mounting joint functions, and relates to the technical field of casing mounting.The outer surface of the casing is fixedly connected with two mounting arms on both sides through reinforcing rib plates, the front part of the casing is provided with a positioning stop, the positioning stop is matched with the front end speed reducer casing to realize assembly positioning, the outer circumferential surface of the positioning stop is provided with a casing mounting flange, a plurality of fastening through holes are uniformly arranged on the casing mounting flange in the circumferential direction to realize fastening connection of the casing and the speed reducer, and the rear part of the casing is provided with a bearing support seat.The application adopts the structure design that a plurality of groups of swing clamping arms are driven by screw rods to circumferentially embrace and clamp, without any professional tool, manual rotation of the adjusting hand wheel can complete quick clamping and fixing and dismounting of the casing and the helicopter platform connecting rod, and solves the industry pain point that the traditional bolt connection has great dismounting difficulty and long time in the narrow installation space.

Description

Technical Field

[0001] This invention relates to the field of casing installation technology, and in particular to a casing for an aero engine that integrates support and mounting functions. Background Technology

[0002] The engine casing is a core load-bearing and functionally integrated component of a turboshaft aero-engine system. It undertakes multiple core functions, including radial and axial support of the rotor system, engine and helicopter platform mounting and fixing, front-end gearbox assembly and positioning, and transmission system protection. Its structural integration, support stiffness, vibration reduction performance, ease of installation, and structural reliability directly determine the aero-engine's operational stability, power transmission accuracy, assembly and maintenance efficiency, and even the overall flight safety of the helicopter. In the demanding application scenarios of helicopter turboshaft engines, the limited installation space places extremely high demands on the casing's lightweight design, multi-functional integration level, and adaptability to complex operating conditions.

[0003] Currently, existing turboshaft engine casings still suffer from technical defects that urgently need to be addressed in practical engineering applications: the disassembly and assembly of the engine to the helicopter platform is cumbersome, resulting in extremely low assembly and maintenance efficiency. Existing engine rear mounting sections generally use a flange bolt-fixed connection structure. During engine installation, maintenance, and disassembly, a large number of fastening bolts need to be tightened or loosened within the confined installation bay of the helicopter. This restricts operating space, increases operational difficulty, and is time-consuming, severely impacting engine assembly and maintenance efficiency. Especially in emergency field maintenance scenarios, rapid disassembly and assembly are impossible, and environmental adaptability is extremely poor.

[0004] In response to the numerous technical deficiencies in the existing technologies, this invention proposes an integrated casing for aero-engines that combines support and mounting functions. This aims to solve the core pain point of cumbersome disassembly and maintenance of existing casings and meet the stringent engineering requirements for the assembly and use of turboshaft aero-engines with helicopter platforms. Summary of the Invention

[0005] The purpose of this invention is to address the shortcomings of existing technologies by proposing an integrated casing for an aero-engine that combines support and mounting functions.

[0006] To achieve the above objectives, the present invention adopts the following technical solution: an integrated support and mounting section for an aero-engine, comprising a disc-shaped outer shell, the outer shell being a hollow structure, two mounting arms being fixedly connected to both sides of the outer surface of the outer shell via reinforcing ribs, a positioning stop being provided at the front of the outer shell, the positioning stop cooperating with the front reducer casing to achieve assembly positioning, a casing mounting flange being provided on the outer circumferential surface of the positioning stop, a plurality of fastening through holes being evenly provided along the circumferential direction on the casing mounting flange to achieve a fastening connection between the casing and the reducer, a bearing support seat being provided at the rear of the outer shell, the bearing support seat mounting the output shaft bearing through a buffer and vibration damping mechanism and providing vibration buffering to achieve a support function, the two mounting arms symmetrically arranged on the left and right sides each forming a rear mounting section of the engine through a quick-release locking mechanism, the quick-release locking mechanism being used to achieve the installation positioning and fastening of the casing and the helicopter platform.

[0007] Preferably, the quick-release locking mechanism includes an internal threaded sleeve, a drive adjustment component, a linkage connection component, and a clamping component. The internal threaded sleeve is fixedly installed on the mounting arm, and the drive adjustment component is threadedly connected to the inner wall of the internal threaded sleeve. The drive adjustment component drives the clamping component to clamp the connecting rod of the helicopter platform through the linkage connection component.

[0008] The effects achieved by the above components are as follows: the internal threaded sleeve provides a stable installation and transmission foundation for the drive adjustment assembly. The drive adjustment assembly, linkage connection assembly, and clamping assembly form a continuous transmission and clamping structure, which can convert the rotation adjustment action into the clamping action, realize the quick clamping and fixing of the helicopter platform connecting rod, and complete the quick disassembly and assembly of the casing and helicopter platform without the need for special tools, which greatly improves the installation and maintenance efficiency of the casing. At the same time, the modular structural design facilitates the inspection and replacement of each component.

[0009] Preferably, the linkage connection assembly includes a plug-in sleeve, the bottom of which is provided with a guide sliding hole, and a plurality of guide sliding rods are slidably connected in the guide sliding hole. The ends of the plurality of guide sliding rods away from the plug-in sleeve are jointly fixedly connected to a linkage tray, and a locking nut is installed on the other side of the linkage tray. Both the linkage tray and the plug-in sleeve are connected to the clamping assembly.

[0010] The effects achieved by the above components are as follows: the plug-in sleeve provides a precise plug-in positioning reference for the connecting rod of the helicopter platform, ensuring the coaxiality of the connecting rod after installation; the sliding fit between the guide slide rod and the guide slide hole provides precise guidance for the lifting and moving of the linkage tray, avoiding the problems of skewing and jamming during the movement of the linkage tray, ensuring the smoothness of the transmission action; the locking nut realizes the rigid connection between the linkage tray and the drive adjustment component, ensuring the stable transmission of transmission power, and thus ensuring the synchronization and consistency of the clamping action.

[0011] Preferably, the clamping assembly includes a linkage rod, and a plurality of linkage rods are hinged to the circumferential surface of the insert sleeve via a hinge joint. A plurality of swing clamping arms are rotatably connected to the outer circumferential surface of the insert sleeve via a hinge pin. Each linkage rod is hinged to one end of a single swing clamping arm, and the other end of each swing clamping arm is fixedly connected to an anti-slip clamping block. The inner wall of the anti-slip clamping block is provided with an anti-slip rubber pad.

[0012] The effects achieved by the above components are as follows: through the hinged linkage structure of the linkage rod and the swing clamping arm, the linear lifting motion of the linkage tray can be converted into the rotational clamping action of the swing clamping arm. The transmission structure is simple and reliable. Multiple sets of swing clamping arms evenly distributed along the circumference can achieve uniform circumferential clamping of the connecting rod. The clamping force is uniform and stable, avoiding problems such as uneven load and loosening during clamping. The anti-slip rubber pad on the inner wall of the anti-slip clamping block can greatly increase the friction between the anti-slip clamping block and the connecting rod, while avoiding scratches on the surface of the connecting rod during clamping, thus improving the safety and reliability of the clamping connection.

[0013] Preferably, the drive adjustment assembly includes a transmission screw, which is threadedly connected to the inner wall of the internal threaded sleeve. The transmission screw passes through the linkage tray and is fixedly connected to the linkage tray through a locking nut. An adjustment handwheel for driving the transmission screw to rotate is fixedly connected to the outer surface of the transmission screw.

[0014] The effects achieved by the above components are as follows: the threaded transmission structure of the transmission screw and the internal threaded sleeve has high transmission accuracy and good self-locking performance, and can achieve stable position locking after clamping, avoiding loosening caused by clamping force attenuation. The adjusting handwheel provides the operator with a convenient manual force application end, and the transmission screw can be manually rotated and adjusted without the need for additional tools. The operation is simple and convenient, which greatly improves the ease of installation of the housing. The locking nut realizes the rigid fixation of the transmission screw and the linkage tray, ensuring the precise synchronization of the adjustment action.

[0015] Preferably, the buffer and vibration damping mechanism includes an upper connecting seat, which is fixedly connected to the bottom of the bearing support seat by bolts. Both sides of the upper connecting seat are obliquely rotatably connected to inclined bracing rods via shafts. The end of the inclined bracing rod away from the upper connecting seat is rotatably connected to the lower mounting base plate via a shaft. A vibration damping component is provided at the bottom of the upper connecting seat, which is used to buffer the vibration generated by the bearing support seat during operation.

[0016] The effects achieved by the above components are as follows: the upper connecting seat provides a stable mounting carrier for the bearing support seat; the symmetrically arranged diagonal bracing rods on both sides form a triangular support structure, providing stable rigid support for the upper connecting seat and ensuring the support rigidity of the bearing support seat; at the same time, the rotational connection structure of the diagonal bracing rods can adapt to the vibration displacement of the upper connecting seat, avoiding rigid interference; and in conjunction with the vibration damping components, it can effectively absorb the vibration impact generated during engine operation, reduce vibration transmission, improve the smoothness of engine operation, and at the same time provide stable support for the output shaft bearing, ensuring the operating accuracy of the output shaft.

[0017] Preferably, the vibration damping assembly includes a damping rod and a buffer spring. The damping rod is composed of an outer sleeve and an inner sliding column slidably connected inside the outer sleeve. The buffer spring is sleeved on the outer surface of the damping rod. The two ends of the buffer spring are fixedly connected to the inner sliding column and the outer sleeve, respectively. One end of the damping rod is hinged to an adjusting member, which is used to adjust the vibration damping amplitude of the vibration damping assembly composed of the damping rod and the buffer spring.

[0018] The effects achieved by the above components are as follows: the buffer spring can effectively absorb the impact energy generated by vibration through elastic deformation, and the damping rod consumes vibration energy through the sliding damping of the inner sliding column and the outer sleeve. The combination of the two can achieve excellent vibration reduction and buffering effect, effectively suppressing vibration and resonance problems during engine operation. The adjusting component can flexibly adjust the buffer amplitude and preload of the vibration damping component, so that the vibration reduction performance can be adapted and adjusted according to different engine operating conditions, greatly improving the adaptability of the casing to operating conditions and the vibration reduction effect.

[0019] Preferably, the adjusting component includes an adjusting screw and a sliding nut seat. A guide cavity is provided on the lower mounting base plate, and the sliding nut seat is slidably connected in the guide cavity. An adjusting screw that passes through the guide cavity is rotatably connected to the lower mounting base plate. The adjusting screw passes through the sliding nut seat and is threadedly connected to the inside of the sliding nut seat.

[0020] The effects achieved by the above components are as follows: the threaded transmission structure between the adjusting screw and the sliding nut seat has high transmission accuracy and can accurately control the movement position of the sliding nut seat. The guide cavity provides precise sliding guidance and circumferential limit for the sliding nut seat, preventing the sliding nut seat from rotating with the adjusting screw and ensuring the accuracy of the adjustment action. The position adjustment of the sliding nut seat can be quickly completed by rotating the adjusting screw, thereby realizing the adjustment of the damping amplitude of the vibration damping component. The adjustment operation is simple and convenient, and online adjustment can be completed without disassembling the components, which greatly improves the convenience of working condition adjustment.

[0021] Preferably, the two ends of the inner sliding column of the damping rod that are opposite to the outer sleeve are respectively hinged to the upper connecting seat and the sliding nut seat through hinges.

[0022] The effects achieved by the above components are as follows: the hinged connection at both ends can adapt to the angle change of the damping rod during the movement of the sliding nut seat, avoiding transmission interference and jamming, ensuring the smoothness of the adjustment action. At the same time, the hinged structure can convert the vertical vibration of the upper connecting seat into the axial extension and retraction of the damping rod, ensuring that the buffer spring and damping rod can fully play their vibration reduction and buffering role, improving the absorption and consumption efficiency of vibration energy, and further optimizing the vibration reduction effect.

[0023] Compared with the prior art, the advantages and positive effects of the present invention are as follows: In this invention, the three core functions of front-end gearbox positioning and installation, bearing support and vibration reduction, and helicopter platform mounting section are integrated into a single cast casing structure. This eliminates the drawbacks of traditional split-type splicing designs, significantly reduces the overall volume and number of parts of the casing, and effectively reduces the overall weight of the engine, perfectly meeting the core design requirements of lightweight aviation equipment. At the same time, the integrated structure eliminates the cumulative errors of multi-component assembly, significantly improves the assembly positioning accuracy of the casing and the coaxiality of the transmission system, and avoids problems such as loose connections and seal failure that occur after long-term operation of spliced ​​structures, greatly improving the reliability and service life of engine operation.

[0024] In this invention, by installing quick-release locking mechanisms at both ends of the support arm, and using a screw drive to drive multiple sets of swing clamping arms for circumferential clamping, the connection between the casing and the helicopter platform can be quickly clamped, fixed, and disassembled without the need for any professional tools. This solves the industry pain point of traditional bolted connections being difficult to install and disassemble in confined installation spaces, and is time-consuming. It significantly shortens the installation and disassembly time of the engine and improves the efficiency of assembly and maintenance. It is especially suitable for emergency field maintenance scenarios and greatly enhances the engine's environmental adaptability.

[0025] In this invention, a triangular support structure is formed by symmetrically arranged diagonal braces on both sides, providing excellent rigid support for the bearing support seat and effectively ensuring the operating accuracy of the output shaft. At the same time, the vibration damping component composed of damping rods and buffer springs can fully absorb the vibration impact generated during the operation of the engine rotor system, significantly reducing the transmission of vibration to the helicopter platform. This not only improves the stability of engine operation but also reduces the wear of precision transmission components and extends the service life of the entire machine. The adjustment component composed of adjusting screws and sliding nut seats can flexibly adjust the buffer amplitude and spring preload of the vibration damping component online, so that the vibration damping performance can be precisely adapted to different flight conditions such as engine takeoff, hovering, and cruise, greatly improving the all-condition adaptability of the casing.

[0026] In this invention, the quick-release locking mechanism adopts a screw thread transmission structure, which has excellent mechanical self-locking performance. After clamping, it can achieve stable position locking. With the help of multiple sets of circumferentially distributed swing clamping arms, it can achieve circumferential uniform clamping of the connecting rod. The clamping force is stable and uniform, and there will be no loosening problem under long-term engine vibration conditions. It avoids the safety hazards of loosening and breakage of traditional bolt connections. The integrated casing structure has uniform stress distribution, avoiding the stress concentration problem of split structures and improving the fatigue resistance of the structure. At the same time, the anti-slip rubber pad on the inner wall of the anti-slip clamping block increases the clamping friction and further absorbs vibration energy, further improving the vibration resistance of the installation connection and comprehensively ensuring the flight safety of the helicopter. Attached Figure Description

[0027] Figure 1 This invention presents a three-dimensional structural diagram of a casing for an aero-engine that integrates support and mounting functions. Figure 2 This invention presents a three-dimensional structural diagram from another angle of an aero-engine casing that integrates support and mounting functions. Figure 3 This invention presents a three-dimensional, disassembled structural diagram of an aero-engine casing that integrates support and mounting functions. Figure 4 This invention provides a structural schematic diagram of a quick-release locking mechanism for an aero-engine casing that integrates support and mounting functions. Figure 5 This invention presents a schematic diagram showing the partial disassembly of the quick-release locking mechanism of an aero-engine casing that integrates support and mounting functions. Figure 6 The present invention provides a schematic diagram of the overall disassembled structure of a quick-release locking mechanism for an aero-engine casing that integrates support and mounting functions; Figure 7This invention presents a schematic diagram of a buffer and vibration reduction mechanism for an aero-engine casing that integrates support and mounting functions. Figure 8 This invention presents a schematic diagram from another angle of the buffer and vibration damping mechanism of an aero-engine casing that integrates support and mounting functions.

[0028] Legend: 1. Locating stop; 2. Casing mounting flange; 3. Fastening through hole; 4. Reinforcing rib; 5. Bearing support seat; 6. Mounting arm; 7. Buffer and vibration damping mechanism; 71. Upper connecting seat; 72. Diagonal brace connecting rod; 73. Lower mounting base plate; 74. Guide slide cavity; 75. Adjusting screw; 76. Sliding nut seat; 77. Vibration damping assembly; 771. Inner sliding column; 772. Outer sleeve; 773. Buffer compression spring; 8. Quick... 81. Locking mechanism; 82. Internal threaded sleeve; 83. Drive adjustment assembly; 84. Transmission screw; 85. Adjustment handwheel; 86. Linkage connection assembly; 87. Locking nut; 88. Linkage tray; 89. Guide slide rod; 80. Insert sleeve; 81. Guide slide hole; 82. Clamping assembly; 83. Linkage pull rod; 84. Swinging clamping arm; 85. Hinge pin; 86. Anti-slip clamping block. Detailed Implementation

[0029] like Figure 1-8 As shown, this invention provides an integrated support and mounting section casing for an aero-engine, comprising a disc-shaped outer shell, which is a hollow structure integrally cast. Reinforcing ribs 4 are symmetrically welded and fixed to the left and right sides of the outer surface of the outer shell. Mounting arms 6 are welded and fixed to the outer ends of each reinforcing rib 4. The two mounting arms 6 are symmetrically arranged along the central axis of the outer shell, forming the main structure of the engine's rear mounting section. A positioning stop 1 is integrally formed at the front of the outer shell. The positioning stop 1 is an annular stop structure, and its inner circular surface mates with the outer stop of the front gearbox, achieving assembly positioning of the casing and the front gearbox. A casing mounting flange 2 is integrally formed on the outer circumferential surface of the positioning stop 1. The casing mounting flange 2 is an annular flange structure, and several fastening through holes 3 are evenly distributed along the circumference of the casing mounting flange 2. The fastening through holes 3 are countersunk through holes, and fastening bolts pass through the fastening through holes 3 to securely mount the entire casing onto the gearbox.

[0030] The rear of the outer casing is integrally formed with a bearing support seat 5, which is a ring-shaped structure. The inner hole of the bearing support seat 5 is used to install the output shaft bearing. The bottom of the bearing support seat 5 is fixedly connected to a damping mechanism 7 by bolts. The damping mechanism 7 is used to provide vibration damping for the output shaft bearing and to achieve radial and axial support for the output shaft. The two mounting arms 6, which are symmetrically arranged on the left and right, are fixedly installed with quick-release locking mechanisms 8 at both ends. The quick-release locking mechanisms 8 constitute the rear mounting section of the engine and are used to achieve quick installation, positioning and fastening connection between the casing and the connecting rod of the helicopter platform mounting frame.

[0031] The quick-release locking mechanism 8 includes an internally threaded sleeve 81, a drive adjustment assembly 82, a linkage connection assembly 83, and a clamping assembly 84. The internally threaded sleeve 81 is welded and fixed to the end of the mounting arm 6. The axis of the internally threaded sleeve 81 is perpendicular to the length direction of the mounting arm 6. The inner wall of the internally threaded sleeve 81 is machined with internal threads. The drive adjustment assembly 82 is threadedly connected to the inner wall of the internally threaded sleeve 81. The drive adjustment assembly 82 includes a transmission screw 821. The external thread of the transmission screw 821 is adapted to the internal thread of the internally threaded sleeve 81. The transmission screw 821 passes through the internally threaded sleeve 81 and is threadedly connected to it. The lower end of the transmission screw 821 passes through the linkage tray 832 of the linkage connection assembly 83. Locking nuts 831 are threadedly connected to the upper and lower sides of the outer surface of the transmission screw 821 on the linkage tray 832. The two sets of locking nuts 831 fasten the transmission screw 821 and the linkage tray 832 together. An adjusting handwheel 822 is fixedly connected to the upper outer surface of the transmission screw 821. The outer circumferential surface of the adjusting handwheel 822 is provided with anti-slip knurling, which is used for the operator to manually rotate and drive the transmission screw 821 to rotate.

[0032] The linkage connection assembly 83 includes a plug-in sleeve 834, which is a hollow cylindrical structure with an open upper end. A guide sliding hole 835 is provided at the center of the lower bottom plate of the plug-in sleeve 834. Several guide sliding rods 833 are evenly slidably connected along the circumferential direction within the guide sliding hole 835. The axes of the guide sliding rods 833 are parallel to the axis of the plug-in sleeve 834. A linkage tray 832 is welded and fixed to the lower ends of the guide sliding rods 833. The linkage tray 832 is a circular disc structure and is coaxially arranged with the plug-in sleeve 834. The outer circumferential surfaces of both the plug-in sleeve 834 and the linkage tray 832 are connected to the clamping assembly 84.

[0033] The clamping assembly 84 includes linkage rods 841. Several linkage rods 841 are evenly hinged along the circumferential direction on the outer circumferential surface of the insert sleeve 834. The upper end of the linkage rod 841 is hinged to the outer wall of the insert sleeve 834 through a hinge member. Corresponding to the position of each linkage rod 841 on the outer circumferential surface of the insert sleeve 834, a swing clamping arm 842 is rotatably connected to it through a hinge pin 843. The hinge pin 843 is horizontally fixed on the outer wall of the insert sleeve 834, and the middle part of the swing clamping arm 842 is rotatably connected to the hinge pin 843. The lower end of a single linkage rod 841 is hinged to the upper end of a single swing clamping arm 842. The lower end of each swing clamping arm 842 is fixedly connected to an anti-slip clamping block 844 by bolts. The anti-slip clamping block 844 has an arc-shaped block structure. An anti-slip rubber pad is glued and fixed to the inner wall of the anti-slip clamping block 844. The surface of the anti-slip rubber pad is provided with anti-slip texture to increase the friction between it and the helicopter platform connecting rod.

[0034] The damping and shock absorption mechanism 7 includes an upper connecting seat 71, which is a rectangular plate structure. The upper surface of the upper connecting seat 71 is fixedly connected to the bottom end face of the bearing support seat 5 by bolts. Both sides of the upper connecting seat 71 are obliquely rotatably connected to inclined bracing rods 72 via shafts. The two inclined bracing rods 72 are symmetrically arranged along the central axis of the upper connecting seat 71. The upper end of the inclined bracing rod 72 is rotatably connected to the side of the upper connecting seat 71 via a shaft, and the lower end of the inclined bracing rod 72 is rotatably connected to the upper surface of the lower mounting plate 73 via a shaft. The lower mounting plate 73 is a rectangular plate structure and is fixedly installed in the internal mounting position of the housing. A damping component 77 is provided at the bottom of the upper connecting seat 71. The damping component 77 is used to dampen the radial and axial vibrations generated during the operation of the bearing support seat 5.

[0035] The vibration damping assembly 77 includes a damping rod and a buffer spring 773. The damping rod consists of an outer sleeve 772 and an inner sliding column 771 slidably connected within the outer sleeve 772. The lower end of the inner sliding column 771 is inserted into the inner hole of the outer sleeve 772 and slides against the inner wall of the outer sleeve 772 to form a damping structure. The buffer spring 773 is sleeved on the outer surface of the damping rod. The upper end of the buffer spring 773 abuts and is fixed to the upper stepped surface of the inner sliding column 771, and the lower end of the buffer spring 773 abuts and is fixed to the lower stepped surface of the outer sleeve 772. An adjusting component is hinged to the lower end of the damping rod. The adjusting component is used to adjust the vibration damping amplitude of the vibration damping assembly 77 composed of the damping rod and the buffer spring 773.

[0036] The adjusting components include an adjusting screw 75 and a sliding nut seat 76. A guide cavity 74 is formed on the upper surface of the lower mounting base 73. The guide cavity 74 is a rectangular long groove structure, and its length direction is consistent with that of the lower mounting base 73. The sliding nut seat 76 is slidably connected within the guide cavity 74, and its outer wall slides against the inner wall of the guide cavity 74, restricting its circumferential rotation. The adjusting screw 75 is rotatably connected to both ends of the lower mounting base 73 via bearing seats. The adjusting screw 75 extends along the length of the guide cavity 74, passing through both end side walls and the middle of the sliding nut seat 76. The external thread of the adjusting screw 75 is compatible with the internal thread of the sliding nut seat 76. The upper end of the inner sliding column 771 of the damping rod is hinged to the bottom center of the upper connecting seat 71 through a hinge, and the lower end of the outer sleeve 772 of the damping rod is hinged to the upper surface of the sliding nut seat 76 through a hinge.

[0037] Working principle: When assembling and using this machine casing, the front positioning stop 1 is first matched with the stop of the front reducer casing to complete the assembly and positioning of the casing and reducer. Then, the fastening bolts are inserted into the fastening through holes 3 on the casing mounting flange 2 and the bolts are tightened to complete the fastening connection between the casing and the reducer. The output shaft bearing is installed in the bearing support seat 5 at the rear. The buffer and vibration damping mechanism 7 provides support and vibration buffer for the bearing, realizing the support function of the casing. The quick-release locking mechanism 8 at both ends of the mounting arm 6 realizes the quick installation and fixation of the casing and the helicopter platform, realizing the installation section function of the casing and completing the integrated assembly of the casing.

[0038] When installing and fixing the casing to the helicopter platform, insert the connecting rod of the helicopter platform into the inner hole of the insertion sleeve 834. The operator manually rotates the adjusting handwheel 822, which drives the transmission screw 821 to rotate. The transmission screw 821 is threadedly engaged with the internal thread sleeve 81. Under the action of threaded transmission, the transmission screw 821 moves upward along the axis of the internal thread sleeve 81. The transmission screw 821 drives the linkage tray 832 to move upward synchronously through the locking nut 831. The linkage tray 832 drives the guide slide rod 833 to slide upward along the guide slide hole 835, ensuring the coaxiality and stability of the linkage tray 832 during movement and avoiding jamming problems.

[0039] When the linkage tray 832 moves upward, it drives the lower end of the linkage rod 841 to move upward. The linkage rod 841 pulls the upper end of the swing clamping arm 842 to swing upward. The swing clamping arm 842 rotates around the hinge pin 843 as the fulcrum, causing the lower end of the swing clamping arm 842 to move closer to the central axis of the insertion sleeve 834. This causes the anti-slip clamping block 844 to tightly hug the outer surface of the helicopter platform connecting rod. The anti-slip rubber pad on the inner wall of the anti-slip clamping block 844 increases the friction between the anti-slip clamping block 844 and the connecting rod, thus achieving a tight connection between the connecting rod and the insertion sleeve 834 and completing the rapid installation and fixation of the casing and the helicopter platform. When disassembly is required, turn the adjusting handwheel 822 in the reverse direction to move the transmission screw 821 downward. This moves the linkage tray 832 to push the linkage rod 841 downward, causing the swing clamping arm 842 to rotate in the reverse direction. This causes the anti-slip clamping block 844 to release the connecting rod, allowing the connecting rod to be pulled out of the insertion sleeve 834, thus completing the disassembly. The disassembly and assembly operations can be completed manually without the need for professional tools, greatly improving the efficiency of the casing's installation and maintenance.

[0040] During the operation of the aero-engine, the vibration generated by the rotation of the output shaft is transmitted to the bearing support 5 through the bearing. The bearing support 5 then transmits the vibration to the upper connecting seat 71. When the upper connecting seat 71 is subjected to vibration and undergoes vertical displacement, it drives the diagonal brace connecting rod 72 to rotate around the shafts at both ends. At the same time, it drives the inner sliding column 771 to slide back and forth within the outer sleeve 772. In conjunction with the elastic deformation of the buffer spring 773, the impact energy generated by the vibration is absorbed. The sliding damping of the damping rod consumes the vibration energy, thereby achieving vibration buffering of the bearing support 5. This effectively reduces the vibration transmission during engine operation, improves the stability and reliability of engine operation, and provides a stable rigid support for the output shaft, ensuring the operating accuracy of the output shaft.

[0041] When it is necessary to adjust the vibration damping amplitude of the bearing support seat 5 according to the engine's operating conditions, the operator rotates the adjusting screw 75. When the adjusting screw 75 rotates, due to the circumferential limiting effect of the guide slide cavity 74 on the sliding nut seat 76, the sliding nut seat 76 slides back and forth in the guide slide cavity 74 along the axis of the adjusting screw 75. When the sliding nut seat 76 moves, it drives the lower end of the damping rod to move synchronously, adjusting the tilt angle between the damping rod and the upper connecting seat 71. At the same time, the damping rod drives the upper connecting seat 71 to produce vertical displacement. In conjunction with the rotation of the diagonal brace connecting rod 72, the distance between the upper connecting seat 71 and the lower mounting base plate 73 is adjusted, thereby adjusting the preload of the buffer spring 773 and the vertical vibration stroke limit of the upper connecting seat 71. This achieves flexible adjustment of the vibration damping amplitude of the bearing support seat 5, enabling the casing to adapt to the vibration reduction requirements under different operating conditions and improving the versatility of the casing.

Claims

1. A casing for an aero-engine that integrates support and mounting functions, characterized in that: The device includes a disc-shaped outer shell with a hollow structure. Two mounting arms (6) are fixedly connected to the outer surfaces of the outer shell by reinforcing ribs (4). A positioning stop (1) is provided at the front of the outer shell. The positioning stop (1) cooperates with the front gearbox to achieve assembly positioning. A casing mounting flange (2) is provided on the outer circumferential surface of the positioning stop (1). Several fastening through holes (3) are evenly opened along the circumferential direction on the casing mounting flange (2) to achieve a fast connection between the casing and the gearbox. A bearing support seat (5) is provided at the rear of the outer shell. The bearing support seat (5) installs the output shaft bearing through a buffer and vibration damping mechanism (7) and provides vibration buffer to achieve the support function. The two mounting arms (6) arranged symmetrically on the left and right are connected at both ends by a quick-release locking mechanism (8) to form the engine rear mounting section. The quick-release locking mechanism (8) is used to realize the installation positioning and fastening of the casing and the helicopter platform.

2. The integrated support and mounting section casing for an aero-engine according to claim 1, characterized in that: The quick-release locking mechanism (8) includes an internal threaded sleeve (81), a drive adjustment assembly (82), a linkage connection assembly (83), and a clamping assembly (84). The internal threaded sleeve (81) is fixedly installed on the mounting arm (6). The drive adjustment assembly (82) is threadedly connected to the inner wall of the internal threaded sleeve (81). The drive adjustment assembly (82) drives the clamping assembly (84) to clamp the connecting rod of the helicopter platform through the linkage connection assembly (83).

3. The integrated support and mounting section casing for an aero-engine according to claim 2, characterized in that: The linkage connection assembly (83) includes a plug-in sleeve (834), the bottom of which is provided with a guide sliding hole (835). Several guide sliding rods (833) are slidably connected in the guide sliding hole (835). The ends of the several guide sliding rods (833) away from the plug-in sleeve (834) are fixedly connected to a linkage tray (832). A locking nut (831) is installed on the other side of the linkage tray (832). Both the linkage tray (832) and the plug-in sleeve (834) are connected to the clamping assembly (84).

4. The integrated support and mounting section casing for an aero-engine according to claim 3, characterized in that: The clamping assembly (84) includes a linkage rod (841). Several linkage rods (841) are hinged to the circumferential surface of the plug sleeve (834) via hinges. Several swing clamping arms (842) are rotatably connected to the outer circumferential surface of the plug sleeve (834) via hinge pins (843). One end of a single linkage rod (841) is hinged to one end of a single swing clamping arm (842). The other end of each swing clamping arm (842) is fixedly connected to an anti-slip clamping block (844). The inner wall of the anti-slip clamping block (844) is provided with an anti-slip rubber pad.

5. The integrated support and mounting section casing for an aero-engine according to claim 4, characterized in that: The drive adjustment assembly (82) includes a transmission screw (821), which is threaded to the inner wall of the internal threaded sleeve (81). The transmission screw (821) passes through the linkage tray (832) and is fixedly connected to the linkage tray (832) through a locking nut (831). An adjustment handwheel (822) for driving the transmission screw (821) to rotate is fixedly connected to the outer surface of the transmission screw (821).

6. The integrated support and mounting section casing for an aero-engine according to claim 5, characterized in that: The buffer and vibration damping mechanism (7) includes an upper connecting seat (71), which is fixedly connected to the bottom of the bearing support seat (5) by bolts. Both sides of the upper connecting seat (71) are connected to inclined bracing rods (72) by shafts. The end of the inclined bracing rod (72) away from the upper connecting seat (71) is rotatably connected to the lower mounting base plate (73) by shafts. The bottom of the upper connecting seat (71) is provided with a vibration damping component (77), which is used to buffer the vibration generated by the bearing support seat (5) during operation.

7. The integrated support and mounting section casing for an aero-engine according to claim 6, characterized in that: The vibration damping assembly (77) includes a damping rod and a buffer spring (773). The damping rod is composed of an outer sleeve (772) and an inner sliding column (771) that is slidably connected inside the outer sleeve (772). The buffer spring (773) is sleeved on the outer surface of the damping rod. The two ends of the buffer spring (773) are fixedly connected to the inner sliding column (771) and the outer sleeve (772) respectively. One end of the damping rod is hinged to an adjusting member, which is used to adjust the vibration buffering amplitude of the vibration damping assembly (77) composed of the damping rod and the buffer spring (773).

8. The integrated support and mounting section casing for an aero-engine according to claim 7, characterized in that: The adjusting component includes an adjusting screw (75) and a sliding nut seat (76). A guide cavity (74) is provided on the lower mounting base plate (73). The sliding nut seat (76) is slidably connected in the guide cavity (74). An adjusting screw (75) that passes through the guide cavity (74) is rotatably connected on the lower mounting base plate (73). The adjusting screw (75) passes through the sliding nut seat (76) and is threadedly connected to the inside of the sliding nut seat (76).

9. The integrated support and mounting section casing for an aero-engine according to claim 8, characterized in that: The inner sliding column (771) of the damping rod and the two ends opposite to the outer sleeve (772) are respectively hinged to the upper connecting seat (71) and the sliding nut seat (76) through hinge members.

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